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针对在被动段脉冲发动机轴向加速变轨突防弹道计算建立了飞行动力模型,通过弹道仿真计算分析了脉冲发动机点火时间和脉冲发动机工作时间对弹道的影响.脉冲发动机总冲一定时,短时间-大推力模式下导弹的射程最大.在爬升段点火时,短时间-大推力导弹能量利用最高;在下降段点火时,长时间-小推力能量利用率最高.同时提出了脉冲轴向加速变轨突防弹道优化的约束条件,并对该问题进行了优化计算,优化后的发动机质量比优化前减少了24.87%.
Aiming at the ballistic acceleration and deceleration trajectory calculation in the passive section pulse engine, the flight dynamics model is established, and the influence of the ignition time of the pulse engine and the pulse engine working time on the trajectory is analyzed by ballistic simulation calculation. - The maximum range of the missile in the large thrust mode is the shortest time when the climbing section is ignited.The energy utilization of the large thrust missile is the highest during the ignition of the descending section and the utilization of the long thrusting energy is the highest The optimization of trajectory and ballistic trajectory optimization constraints, and the optimization of the problem, the optimized engine mass than before optimization reduced by 24.87%.